Nozzle-vane band for a gas turbine engine
US6830427B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Nov 26, 2002 |
| Grant date | Dec 14, 2004 |
| Priority date | — |
| Expiry date | Nov 26, 2022 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF01D5/187
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A high-pressure turbine nozzle-vane band for a gas turbine engine. The band includes an inside surface supporting at least one guide vane having a trailing edge that is directed towards a downstream end of the band, and an outside surface, opposite the inside surface, from which a flange extends radially, defining firstly, upstream from the flange, a passage for cooling-air, and secondly, downstream from the flange, a cavity. The inside surface of the band is provided, between the trailing edge of the guide vane and the downstream end of the band, with a coating forming a thermal barrier enabling a temperature gradient generated in the band by the air spinning in the cavity to be increased.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.